Method of deriving power from explosive gases and in gas turbine apparatus



Dec. 12,1933; F. M. BROOKE I 1,933,635 METHOD OF DERIVING POWER FROMEXPLOSIVE GASES AND IN GAS TURBINE APPARATUS Filed Aug; 18, 1931 5Sheets-Sheet 1 TTORNEYS.

Dec. 12, 1933. F, M, Emma 1,938,686

METHOD OF DERIVING POWER FROM EXPLOSIVE GASES AND IN GAS TURBINEAPPARATUS Filed Aug. 18, 1931 5 Sheets-Sheet 2 WITNESSES 12, 1933- F. M.BROOKE 7 1,938,686

METHOD OF DERIVING POWER FROM EXPLOSIVE GASES AND IN GAS TURBINEAPPARATUS Filed Aug. 18, 1931 5 Sheets-Sheet 3 wmvzgsg 7 2 Dec. 12,1933; F, M, ROOKE 1,938,686

METHOD OF DERIVING POWER FROM EXPLOSIVE GASES AND IN GAS TURBINEAPPARATUS Filed Aug. 18, 1931- 5 Sheets-Sheet 4 INVENTOR:

Dec. 12,1933. BROOKE 1,938,686

METHOD OF DERIVING POWER FROM EXPLOSIVE GASES AND IN GAS TURBINEAPPARATUS Filed Aug. 18, 1951 5 Sheets-Sheet s 1 16.2? 1171105176flmmkrl Explosive C/ZamkrZ flx vioszue amber Li WITNESSES V I N VEN TOR:

.MnwMfimoire Patented Dec. 12, 1933 UNITED STATES PATENT OFFICE METHODOF DERIVING POWER FROM" EXPLOSIVE GASES AND IN GAS TURBINE APPARATUSApplication August 18, 1931.

7 Claims.

This invention relates to the derivation of power from explosive gases,as well as to turbines designed for use of explosive gases as the mediaof motivation.

The main object of my invention is to make possible efficientutilization of explosive gases in operating prime movers, particularlyof the of the rotary or turbine type, with a view toward avoiding directimpingement of flame attending combustion of the gases upon the movingparts. In connection with turbines, I attain this desideratum throughprovision of a chamber or chambers wherein the combustible gases areinitially confined and exploded, and from which the flow of theexpanding gases to the turbine, is automatically controlled in suchmanner that a substantially continuous kinetic stream at constantpressure is available for action upon the turbine rotor.

My invention is further directed toward the provision of means wherebywater or other fluent cooling medium is continuously circulated undercentrifugal action through and around the blades of both the stator andthe rotor of the turbine, so that these parts are maintained amply coolfor capacity to resist warping or distortion under the action of the hotexpanding gases.

Still other objects and attendant advantages of this invention will bemanifest from the following description taken in connection with theattached drawings, wherein Fig. I is an illustration, partly in sideelevation and partly in longitudinal section, of a gas turbine apparatussuitable for operation under my improved method.

Fig. II is a plan view of the organization.

Fig. III is an elevation of the left hand end of the apparatus asconsidered in respect to Figs. I and II.

Fig. IV is an elevation of the right hand end of the turbine structurelikewise as considered in respect to Figs. I and II.

Fig. V is a horizontal fragmentary plan sectional view through thechambers in which the gases are exploded previous to conduction into theturbine proper, the section being taken as indicated by the arrows V-Vin Fig. I.

Fig. VI is an axial sectional view through one of the explosion chamberstaken as indicated by the arrows VI-VI in Figs. I and V.

Fig. VII is a fragmentary detail view taken as indicated by the arrowsVII-VII in Fig. I showing the relative arrangement of the stator androtor blades of the turbine.

Serial No. 557,816

Fig. VIII is a diagrammatic view showing the drive means for the valvescontrolling the flow of the expanding gases from the explosion chambersto the turbine; and,

Fig. IX is a diagram showing the relative 60 positions of the severalexplosion chambers.

With more detailed reference to these illustrations, the explosionchambers hereinbefore referred to are, in the present instance, three innumber, and respectively designated by .the numerals 1, 2 and 3. Asshown, these explosion chambers 1-3 are in the form of verticalcylinders cast enblock; and supported upon a pedestal 4 upstanding froma base 5, adjacent the turbine which is comprehensively designated bythe numeral 6. Leading to fuel induction ports '7,

8 and 9 at the front of the explosion chambers 1, 2 and 3 near the topsof the latter, is an intake manifold 10 whereof the open end is flaredinto the form of an annular casing 11 which houses a rotary disk fan 12.The shaft 13 of this disk fan 12 is connected, with interposition of aclutch conventionally indicated at 14 in Figs. I and II, to an electricmotor 15, which, together with the fan housing 11 is supported by alateral shelf 16 of the explosion chamber block. Liquid fuel such asgasoline is introduced into a duct 18 axially of the fan shaft 13. Asshown in Fig. I, the fan shaft 13 terminates at its inner end in a head20 with a series of radial nozzles 21 from which the liquid fuel issprayed by centrifugal action, into the stream of air blown underpressure into the manifold 10 by the fan 12. At their opposite sides andat a level below the induction ports the explosion chambers 1, 2 and 3are provided with outlet ports 22, 23 and 24 which open into a. manifold25 that connects axially into the rear of the turbine 6, as shown inFigs. I and II. Adjacent their lower ends and on the side occupied bythe fuel induction manifold 10, the explosion cylinders 1, 2 and 3 aremoreover provided with smaller exhaust ports 27, 28 and 29 respectively,which, in turn, open into a manifold 30 connecting with what I term anindependent exhaust 31 around the stator 32 of the turbine 6. Rotativewithin the explosion chambers 1, 2 and 3 are rotary valves 33, 34 and 35with ports 36,37 and 38, respectively, at the level of the fuelinduction ports '7, 8 and 9; as well as with ports 39, 40 and 41 (Fig.IX) at the level of the discharge ports 22, 23 and 24. The valves 33-35are further provided near their bottoms with ports 42, 43 and 44 at thelevel of the residue exhaust ports 27, 2a and 20 of the explosionchambers 1-3. The cylindric valves 33-35 substantially occupy thechambers 1-3 and have closed-in bottoms. for a purpose later explained.The charges of fresh gaseous fuel admitted successively into thechambers l-3 are exploded in definite succession, as hereinafter morefully explained, by -means of spark plugs 48 at the tops of the saidchambers under control of a suitable timer or distributor, notillustrated.

From Fig. I it will be noted that the stator 32 of the turbine 6 ispreferably of hollow horseshoe cross-sectio'nal or hollow semi-sphericalconfiguration and affords a continuous passage 49 for the exploded gasesfrom the manifold 25 to the stator blades 50, which are arranged as anannular series for flow of the gases horizontally rearward between them.Also as shown in Fig. I, the turbine stator 32 affords an inwardtapering annular hollow 51 to receive the correspondingly configuredrotor designated 52, with a working fit. The walls of the stator 32 arejacketed as at 53 and 54, the jacketings being extended to the top andbottom ends of the stator blades 50 which are vertically hollow. Afluent cooling medium, such as water, is introduced into the lower partof the stator jacketing 53, 54 through a pipe 55, and, after circulatingupward through the stator 32 and its hollow blades 50, is dischargedthrough a pipe 56 at the top. Part of the water introduced into thestator 32 as just explained, is circulated through communicatingjacketings 5'7 and 58 respectively around the manifold 25 and theexplosion chambers 1, 2 and 3 to cool these parts also. It is to beparticularly noted that I make the stator 32 of horse-shoe cross-sectionin order to direct the exploded gases horizontally through the hollowstator blades 50 to increase the efficiency of the turbine as well as tocounteract circumferential expanding tendencies.

Referring again to Fig. I, the rotor 52 has an internal spider 60 with acentral hub 61 engaging the shaft 62 of the turbine 6, which shaft issupported at its opposite ends in bearings 63 and 64. The bearing 63 itwill be noted is integrally formed centrally of the axial cavity of thestator 32; while the bearing 64 is afforded by a standard 65 bolted orotherwise secured to the base 5 of the apparatus. As shown in Figs. Iand VII the rotor 52 is provided with two annularly arranged sets ofblades 66 and 67 which are disposed at an angle, in respect to thestator blades 50, and spaced by a substantial interval 68. Like thestator blades 50, the rotor blades 66 and 67 are made vertically hollowand communicate, by way of connecting passages 69, for circulation ofwater which is conducted to and away from said blades by way of flow andreturn ducts '70 and '71 from an annularly hollow frusto-conicalradiator '72 which is attached in axial relation to the frontal end ofthe rotor 52 and which converges away from the rotor blades 67.Continuous water circulation between the radiator 72 and the rotor '52is automatically maintained by combined thermal and centrifugal actionwhich is promoted as a consequence of the described configuration ofsaid radiator. In other words, the colder water of higher specificgravity in the radiator '72 is forced radially outward under centrifugalaction, and thereby presses the warmer water of lower specific gravityinward with resultant maintenance of a constant flow of the coolingmedium as aforesaid.

After passinghorizontally through the blades 50 and 66, 6'7 respectivelyof the rotor 52 and the stator 32, the spent gases are conducted to thecircumferential hollow 31 around the stator 32 by way of a continuousannular passage 73 of semi-circular cross-section afforded by the rotor52, said passage terminating in an annular part '73 having a radialbearing in a counter-bore 31' of the stator 32, see Fig. I. From thecircumferential chamber 31 of the stator 32 the spent gases are finallycarried off to a point of disposal through a number of pipes '74connecting radially into said chamber. The continuous annularsemi-circular cross-section of the rotating annular passage '73 servesto accelerate effective exhaust of the spent gases under centrifugalaction, as well as to eliminate setting-up of back pressure while takingcare of vibration and expansion. Suitable packing rings '75, '76, '77and 78 are interposed between the coacting parts of the stator 32 androtor 52 of the turbine 6 to prevent gas leakage. At this juncture it isto be remarked that I make use of the packings '75- 78 to preventleakage of carbon-monoxide gas, to maintain pressure when the exhaustgas is to be further utilized, while avoiding the possibility 100 of anyback pressure tending to accentuate leakage if such packings were notemployed; but it will be apparent said packings may be dispensed with ifthe coacting parts are finished to a nonleakage fit.

Normally, the fuel induction fan 12 is driven from the shaft 62 of theturbine 6 through means including a bevel gear 80 which is secured tothe said turbine shaft adjacent its inner end, and which meshes with abevel pinion 81 on a ver- 110 tical shaft 82 with journal support insuitable bearings 83, 84 afforded by the turbine stator 32. A miterpinion 85 at the upper end of the vertical shaft 82 communicates themotion of the latter, through an intermeshing miter 86 to a 115horizontal shaft 87 which rotates in bearing brackets 88 and 89 boltedor otherwise secured to the explosion chamber block. As shown in Figs. Iand II, the shaft 87 extends forwardly over the top of the explosionchambers l, 2 and 3 for coordination, through a sprocket chain 90 withthe shaft 13 of the fan 12. Still referring to Fig. I, the bevel gears80 and 81 run in an oil chamber 91 provided within the axial cavity ofthe stator 32. The miter pinions 85, 86 are in a like manner encased ina housing 92 bolted to the top of the turbine stator 32, said housing 92being kept well filled with lubricant.

The sleeve valves 33-35 in the chambers 1-3 are driven in unison and inproper timed rela- 1 tion with the rotation of the turbine shaft 62through a sprocket chain connection 93, from the overhead shaft 8'7, toa horizontal shaft 94 which is journalled in suitable bearings at thebottom of the explosion chamber block. Referring to Figs. I, VI and VIIIthe shaft 94 is fitted with worms 95, 96 and 97 which mesh respectivelywith worm wheels 98, 99 and 100 around the closed-in or integrallyformed bottom ends of the sleeve valves 33, 34 and 35. The worm gearing140 95100 just referred to operates in lubricant contained in anencasing hollow 101 jointly afforded by the explosion chamber block andthe pedestal 4 whereon the latter is supported. It is to be noted thatthe sleeve valves 33-35 are purpose- 5 1y formed with substantialbottoms and that the integrally-formed worm wheels 98-100 seat onaligning axial embossments of the pedestal 4 in abutting relation to thelower ends of the chambers-1-3, as clearly understandable from Fig, VI150 more particularly, whereby escape of-exploded ases about the valves33-35 is reduced to a minimum, and the necessity of furnishing saidvalves with packing rings is eliminated. Furthermore, the closed valvebottoms serve as thrust-bearings, as well as. providing a substantialcontact area for cooling conduction.

The operation of the turbine apparatus is as follows:

The turbine 6 is initially set in motion by means of the electric motor15 through the clutch 14, which may be either of a hand type or of anautomatic type capable of disconnecting the motor 15 after the turbine 6has started under its own power. With continuous rotation of the fan 12,atmospheric air is sucked into the fan housing 11 and mingles with theliquid fuel concurrently discharged from the nozzles 21 of the head 20on the inner end of the fan shaft 13, to vaporize the latter and formthe explosive gas. By the manifold 10, the fuel and air mixture or gasis conducted to the cylindric explosion chambers l, 2 and 3. The valves33, 34 and 35, being driven in unison by the worm gearing 95-100 ashereinbefore described, admit charges of the fresh fuel mixturesuccessively into the chambers l, 2 and 3 by way of their ports 36, 37and 38 when the. said ports register with the ports '7, 8 and 9 of saidchambers. The freshly inducted charges are exploded likewise in definitesuccession, and, immediately upon being exploded, are released throughthe valve ports 39, 40 and 41 into the manifold 25 for conduction to theturbine 6. During the time of charging of the several chambers 1, 2 and3 with fresh fuel mixture, the ports 42, 43 and 44 of the sleeve valves33, 34 and 35 are open to exhaust any previously exploded residueremaining within the said chambers, such exhaust being conducted to thecircumferential chamber 31 around the turbine stator 32 by the manifold30 for disposal, through the pipes 74, with the spent gases dischargedby the turbine 6. How the sequential charging of the explosion chambers1, 2 and 3 and the release of the gases from them after explosion iseffected will be readily understood upon reference to Fig. IX which isto be read downward.

As shown in Fig. IX, a fresh charge of fuel gas is being admitted intoexplosion chamber 1 through the inlet port 36 of the sleeve valve 33,the outlet port 39 being at this time closed, but the port 42 part wayopen for escape of any residue from the previous explosion. At the sameinstant, all the ports 37, 40 and 43 of the explosion chamber 2 areclosed while the charge of gas in the said chamber is being exploded.Contemporaneous with the aforedescribed conditions in chambers 1 and 2,the induction and residue exhaust ports 38 and 44 of chamber 3 are bothclosed, but the discharge port 41 open to release an exploded chargeinto the manifold 25. The sleeve valves 33, 34 and 35 are of coursecyclic in their operation so that a substantially steady stream of theexpanding exploded gas is conducted into the turbine 6 to motivate it.In all instances, the explosions take place immediately before thedischarge ports 39, 40 and 41, of the explosion cylinder sleeve valves33, 34 and 35 open, so that the flame flashes attending the explosionsordinarily do not affect the stator and rotor vanes 50 and 66, 67, ofthe turbine 6, said vanes being thereby protected against warping orburning. The constant passage of water through the turbine blades 50, 66and 67, in the manner already understood acts to further safeguardagainst'the contingencies mentioned.

With an apparatus such as described operating under my novel method, itis thus possible to create motion with conservative use of gaseous fueland at the same time preclude injury to the moving parts of the primemover.

Having thus described my invention, I claim:

1. In gas turbine apparatus comprising a multiplicity of separateexplosion chambers, and a turbinein communication with said chambers bya common manifold; continuously rotative valve means substantiallyoccupying and closing-in the associated explosion chamber at one endwhile providing thrust-bearing for the former, said valve meanscontrolling induction of fuel gas successively into the severalexplosion chambers and subsequently releasing the successively explodedcharges from the said chambers in a substantially continuous keneticstream into the turbine.

2. In gas turbine apparatus comprising a multiplicity of cylindrioexplosion chambers, and a turbine in communication with the explosionchambers by a common manifold; individually associated coordinativelyoperated continuously rotating rotary valves substantially occupying andclosing-in the explosion chambers at one end while providingthrust-bearing therefor, said valves controlling successive induction ofthe gas charges into said explosion chambers and release of such chargessuccessively, after explosion, in a substantially continuous kineticstream into the turbine.

3. In gas turbine apparatus comprising a multiplicity of cylindricexplosion chambersand a turbine in communication with the explosionchambers by a common manifold; individually associated rotary valvescontinuously driven in unison by the turbine, said valves havingclosedin lower ends affording thrust-bearing therefor and substantiallyoccupying the explosion chambers with inlet ports controlling successiveinduction of the gas charges into the explosion chambers and exhaustports for release of such charges successively, after explosion, in asubstantially continuous stream into the turbine.

4. In gas turbine apparatus comprising a multiplicity of separateexplosion chambers, and a turbine in communication with the explosionchambers by a common manifold; individually associated valves havingclosed-in lower ends in the respective explosion chambers, said closedinlower ends affording thrush-bearing for the valves and preventing gasleakage thereabout, worm gear mechanism coordinating said valves fordefinite actuation in controlling induction of successive charges offuel gas into the explosion chambers, said valves having auxiliaryexhaust ports to concurrently release previously exploded gas from thechambers, and main exhaust ports for subsequent release of the freshlyexploded charges in a substantially continuous stream into the turbine;

5. A gas turbine comprising a stator of hollow horse-shoecross-sectional configuration with a circumferential exhaust chamber andan inwardly tapering annular cavity, hollow blades in the stator havingdirect connection with said stator hollow, a correspondingly taperedrotor with hollow blades annularly arranged for horizontal projection ofthe motivating gas through the intervals between them, means providing acontinuous pasage of semi-circular cross-section about the rotor toreceive the spent gas upon leaving the rotor blades. and a radiatorattached to and axially rotatable with the rotor and havingcommunication into the hollow blades by way of connecting flow andreturn passages, said radiator being in the form of a coaxial hollowcone convergent toward the rotor axis from the turbine blades andoperating to continuously circulate cooling medium therethrough bycombined thermal and centrifugal action.

6. A gas turbine comprising a stator of hollow horse-shoecross-sectional configuration having an inwardly-tapering annular cavityat its open end with a surrounding exhaust chamber. said stator havingblades affording flowcommunication between the hollow and cavity, saidhorse-shoe cross-sectional formation of the stator serving to direct themotivating gas horizontally through said blades, acorrespondinglyconfigured rotor with angularly disposed hollow bladesannularly-arranged in spacial parallelism for similar projection of themotivating gas through the intervals between them, and means providing acontinuous passage of semi-circular cross-section circumferentially ofand integral with the rotor to receive the spent gas upon leaving therotor blades, said means having rotary bearing in the stator and servingto accelerate discharge of the spent gas directly through the exhaustchamber.

7. A gas turbine comprising a stator of hollow horse-shoecross-sectional configuration having an inwardly-tapering annular cavityat its open end with a surrounding exhaust chamber, said stator havingblades affording direct flow-communication between the hollow andcavity, said horse-shoe cross-sectional formation of the stator servingto direct the motivating gas horizontally through said blades, 2.correspondingly-configured rotor with angularly disposed hollow bladesannularly-arranged in spaial parallelism for similar projection of themotivating gas through the intervals between them, means providing acontinuous passage of semicircular cross-section circumferentially ofand integral with the rotor to receive the spent gas upon leaving therotor blades and serving to accelerate discharge of said spent gas, saidmeans having rotary bearing at its outer portion in the statoraforesaid, and suitable packing interposed between the coacting parts ofthe stator and rotor to prevent leakage of gas fumes thereat.

FRANCIS M. BROOKE.

